JPH0751888B2 - Cooling shroud support - Google Patents
Cooling shroud supportInfo
- Publication number
- JPH0751888B2 JPH0751888B2 JP4019345A JP1934592A JPH0751888B2 JP H0751888 B2 JPH0751888 B2 JP H0751888B2 JP 4019345 A JP4019345 A JP 4019345A JP 1934592 A JP1934592 A JP 1934592A JP H0751888 B2 JPH0751888 B2 JP H0751888B2
- Authority
- JP
- Japan
- Prior art keywords
- hanger
- outlet
- shroud support
- shroud
- fluid
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
【0001】[0001]
【産業上の利用分野】本発明はガスタービンエンジンの
翼端とシュラウドとの間隙の制御に関し、特に、間隙制
御を改善するように冷却されるシュラウド支持体に関す
る。FIELD OF THE INVENTION The present invention relates to gas turbine engine tip to shroud clearance control, and more particularly to a shroud support which is cooled to improve clearance control.
【0002】[0002]
【従来の技術】従来のガスタービンエンジンは周方向に
相隔たる多数の動翼を備えたタービンを含み、動翼の先
端は環状の静止シュラウドから半径方向内方に離隔して
それとの間に間隙を画成する。翼端間隙をなるべく小さ
くすることにより動翼周囲の燃焼ガスの漏れを最少にし
てタービンの効率を高める必要がある。しかし、運転中
の翼端間隙は、動翼とシュラウドとの熱膨縮差に適応し
て両者間の望ましくない摩擦を防ぐのに充分な程大きく
なければならない。BACKGROUND OF THE INVENTION A conventional gas turbine engine includes a turbine having a number of circumferentially spaced blades, the tips of the blades being spaced radially inward from a stationary annular shroud and having a gap therebetween. Define. It is necessary to minimize the leakage of combustion gas around the moving blades and improve the efficiency of the turbine by making the tip clearances as small as possible. However, the tip clearance during operation must be large enough to accommodate the differential thermal expansion and contraction of the blade and shroud to prevent unwanted friction between them.
【0003】翼端間隙は、従来、エンジンの様々な定常
運転状態において様々な値をもち、また、エンジン出力
値を変えるにつれて発生するエンジンの様々な過渡運転
状態中も様々な値を取る。過渡翼端間隙制御は重要な問
題である。なぜなら、翼端とシュラウドとの熱差動は、
翼端摩擦のおそれを減らすために適度に大きくすべき最
小値をもつからで、この最小値は狭点(pinch point)の
値とも呼ばれる。しかし、狭点の値を適度に大きくして
も、過渡応答における他の時点と、定常状態の運転中と
に発生する翼端間隙は狭点より必ず大きいので、翼端を
通り越す燃焼ガスの漏れを増加させてタービン性能を減
らす。Tip clearances conventionally have different values under different steady-state operating conditions of the engine, and also during different transient operating conditions of the engine which occur as the engine power value is varied. Transient tip clearance control is an important issue. Because the thermal differential between the blade tip and the shroud is
This minimum value is also called the pinch point value because it has a minimum value that should be reasonably large to reduce the risk of tip friction. However, even if the value of the narrow point is moderately increased, the blade tip clearance that occurs at other points in the transient response and during steady-state operation is always larger than the narrow point, so the leakage of combustion gas past the blade tip To reduce turbine performance.
【0004】さらに、ガスタービンエンジンは通例軸対
称であるが、タービンシュラウドの環境における温度は
エンジン中心線について周方向に必ずしも均等ではな
い。例えば、回収熱交換器を含むガスタービンエンジン
の一例では、圧縮機吐出し空気が回収熱交換器により加
熱され、そして高圧タービン(HPT)のシュラウド近
辺でエンジンケーシングの頂部と底部近くに配置した2
つの周方向に相隔たる回収熱交換器導管を経て燃焼器に
導かれる。従って、HPTシュラウドは、温度がほぼ周
方向で変わる環境に配置され、比較的高い温度が回収熱
交換器導管の近くで発生しそして比較的低い温度が両導
管の間で発生する。従って、HPTの翼端間隙は、周方
向に均等な冷却空気をシュラウドに供給する従来のよう
に冷却されるシュラウド支持体の場合、エンジン中心線
について周方向に一様でない。Moreover, although gas turbine engines are typically axisymmetric, the temperature in the turbine shroud environment is not necessarily uniform circumferentially about the engine centerline. For example, in one example of a gas turbine engine that includes a recovery heat exchanger, the compressor discharge air is heated by the recovery heat exchanger and is located near the top and bottom of the engine casing near the high pressure turbine (HPT) shroud.
It is led to the combustor via two circumferentially separated recovery heat exchanger conduits. Therefore, the HPT shroud is placed in an environment where the temperature varies substantially circumferentially, with relatively high temperatures occurring near the recovery heat exchanger conduit and relatively low temperatures occurring between both conduits. Thus, the HPT tip clearance is not circumferentially uniform about the engine centerline for conventionally cooled shroud supports that provide circumferentially uniform cooling air to the shroud.
【0005】[0005]
【発明の目的】従って、本発明の目的は、翼端間隙の周
方向変動を減らすために周方向において比較的均等に冷
却されるシュラウド支持体を提供することである。OBJECTS OF THE INVENTION Accordingly, it is an object of the present invention to provide a shroud support that is relatively evenly cooled in the circumferential direction to reduce circumferential variations in tip clearance.
【0006】[0006]
【発明の概要】シュラウド支持体が、環状ケーシング
と、このケーシングから半径方向内方に離隔した環状ハ
ンガとを含む。ハンガは、その内部に周方向に延在する
流れダクトを有し、また複数の周方向に相隔たるタービ
ン動翼の半径方向外側に配置し得るシュラウドを半径方
向に支持するベースを有する。冷却流体をハンガの流れ
ダクト内で周方向に導くことによりハンガを冷却し、こ
うして、周方向翼端間隙の均等度を高めるとともに、シ
ュラウドと翼端との熱変位をより良く整合する。SUMMARY OF THE INVENTION A shroud support includes an annular casing and an annular hanger radially inwardly spaced from the casing. The hanger has a circumferentially extending flow duct therein and also has a base radially supporting a plurality of circumferentially spaced shrouds that may be disposed radially outward of the turbine blades. Cooling the hanger by guiding cooling fluid circumferentially within the hanger's flow duct thus increasing the uniformity of the circumferential tip clearance and better matching the thermal displacement between the shroud and the tip.
【0007】本発明は、他の目的と利点とともに、添付
図面と関連する以下の詳述からさらに明らかとなろう。The invention, together with other objects and advantages, will be more apparent from the following detailed description in conjunction with the accompanying drawings.
【0008】[0008]
【実施例の記載】図1はガスタービンエンジンの一例1
0の概略図である。エンジン10には従来の圧縮機14
と環状燃焼器16と高圧タービンノズル18と高圧ター
ビン(HPT)20と低圧タービン(LPT)22が含
まれ、直流連通をなしかつエンジンの軸方向中心線12
の周りに同軸的に配置されている。従来のHPT軸24
が圧縮機14をHPT20に連接し、そして従来のLP
T軸26がLPT22から突出して負荷(図示せず)に
動力を伝える。DESCRIPTION OF THE EMBODIMENTS FIG. 1 shows an example 1 of a gas turbine engine.
FIG. The engine 10 has a conventional compressor 14
And an annular combustor 16, a high pressure turbine nozzle 18, a high pressure turbine (HPT) 20 and a low pressure turbine (LPT) 22, which are in direct current communication and which have an axial centerline 12 of the engine.
Are arranged coaxially around. Conventional HPT shaft 24
Connects the compressor 14 to the HPT 20, and the conventional LP
The T shaft 26 projects from the LPT 22 and transmits power to a load (not shown).
【0009】エンジン10はさらに環状ケーシング28
を含み、このケーシングは圧縮機14を覆いそこから下
流に延びてLPT22を覆っている。従来の回収熱交換
器30がケーシング28の外側に圧縮機14とLPT2
2の間に配置されている。The engine 10 further includes an annular casing 28.
This casing covers the compressor 14 and extends downstream therefrom to cover the LPT 22. The conventional recovery heat exchanger 30 has the compressor 14 and the LPT 2 outside the casing 28.
It is located between two.
【0010】エンジン10の従来の運転中、周囲空気3
2が圧縮機14に入って圧縮され圧縮空気流34とな
る。圧縮空気流34は従来のように適当な導管30aを
経て回収熱交換器30を通り、そこでさらに加熱された
後、適当な導管30bを経てケーシング28を貫流し燃
焼器16近辺に導かれる。加熱された圧縮空気流34は
図2において回収熱交換器空気流34bとして示されて
いるもので、その後燃焼器16内で従来のように燃料と
混合して点火され、その結果燃焼ガス36が発生しノズ
ル18を経てHPT20に入る。HPT20は燃焼ガス
36からエネルギーを抽出しHPT軸24を介して圧縮
機14を駆動し、その後燃焼ガス36はLPT22に達
する。LPT22はさらに燃焼ガス36からエネルギー
を抽出し、LPT軸26に連結した負荷(図示せず)を
駆動する。回収熱交換器30は従来のように導管30c
によりLPT22に接続され、燃焼ガス36の一部分が
LPT22から回収熱交換器30に導入され、同熱交換
器を通流する圧縮空気流34を加熱する。During conventional operation of engine 10, ambient air 3
2 enters the compressor 14 and is compressed into a compressed air stream 34. Compressed air stream 34 passes through suitable conduit 30a through recovery heat exchanger 30 as is conventional, where it is further heated and then flows through casing 28 through suitable conduit 30b into the vicinity of combustor 16. The heated compressed air stream 34, shown in FIG. 2 as the recovered heat exchanger air stream 34b, is then conventionally mixed with fuel in the combustor 16 and ignited, resulting in combustion gas 36. It is generated and enters the HPT 20 through the nozzle 18. The HPT 20 extracts energy from the combustion gas 36 and drives the compressor 14 via the HPT shaft 24, after which the combustion gas 36 reaches the LPT 22. The LPT 22 further extracts energy from the combustion gas 36 and drives a load (not shown) connected to the LPT shaft 26. The recovery heat exchanger 30 has a conventional conduit 30c.
Is connected to the LPT 22, and a part of the combustion gas 36 is introduced from the LPT 22 to the recovery heat exchanger 30 to heat the compressed air flow 34 flowing through the heat exchanger 30.
【0011】図1に示すように、2本の回収熱交換器導
管30bが約180度離れた角位置でケーシング28に
接続されている。エンジン10の運転中、加熱された回
収熱交換器空気流34bは両導管30bを通ってケーシ
ング28内に入り燃焼器16と高圧ノズル18とHPT
20の上流端との近辺に達する。両導管30bは180
度離れているので、ケーシング28内の温度は周方向に
沿って変わり、最高温度が両導管30bの近くで生じそ
して最低温度が両導管30b間のほぼ等角度または等距
離の位置で発生する。As shown in FIG. 1, two recovery heat exchanger conduits 30b are connected to the casing 28 at angular positions about 180 degrees apart. During operation of the engine 10, the heated recovery heat exchanger airflow 34b enters the casing 28 through both conduits 30b and the combustor 16, high pressure nozzle 18 and HPT.
Reach the vicinity of the upstream end of 20. Both conduits 30b are 180
Because of the degrees of separation, the temperature within casing 28 varies circumferentially, with the highest temperatures occurring near both conduits 30b and the lowest temperatures occurring at approximately equiangular or equidistant locations between both conduits 30b.
【0012】従って、ケーシング28内のHPT20近
辺の環境温度のこの周方向変化は、動翼44とシュラウ
ド42との熱応答差と、翼端間隙の周方向変化とを減ら
す本発明によって提供されるような適当なシュラウド支
持体を必要とする。Thus, this circumferential change in ambient temperature near the HPT 20 within the casing 28 is provided by the present invention which reduces the thermal response difference between the blade 44 and the shroud 42 and the circumferential change in tip clearance. Such a suitable shroud support is required.
【0013】さらに詳述すると、図2に示すように、エ
ンジン10は本発明の一実施例によるタービンシュラウ
ド支持体38をさらに含み、このシュラウド支持体は複
数の周方向に相隔たるボルト40によりケーシング28
に従来のように固定され支持されている。従来の環状タ
ービンシュラウド42が、例えば複数の周方向に相隔た
るシュラウド部片の形態をなすものとして、従来のよう
にシュラウド支持体38に結合されており、そしてHP
T20の第1段の複数の動翼44から半径方向に所定の
ように隔たっている。各動翼44は翼端44bを有し、
この翼端はシュラウド42から半径方向内方に離隔して
翼端間隙Cを画成する。More specifically, as shown in FIG. 2, engine 10 further includes a turbine shroud support 38 according to one embodiment of the present invention, the shroud support being casing by a plurality of circumferentially spaced bolts 40. 28
It is fixed and supported in the conventional manner. A conventional annular turbine shroud 42 is conventionally coupled to shroud support 38, for example in the form of a plurality of circumferentially spaced shroud pieces, and HP
It is separated from the plurality of blades 44 of the first stage of T20 in the radial direction by a predetermined distance. Each blade 44 has a tip 44b,
The tip is spaced radially inward from shroud 42 to define a tip clearance C.
【0014】シュラウド支持体38には環状ハンガ46
が含まれ、中心線12の周りに同軸的に配置されてお
り、この中心線はシュラウド支持体38の中心線でもあ
る。ハンガ46は、ほぼ円錐台形の一体の環状取付けフ
ランジ48によりケーシング28に固定されている。こ
のフランジは環状流路50内でハンガ46をケーシング
28から半径方向内方に隔てており、環状流路50はケ
ーシング28とそれから半径方向内方に離隔した諸構成
部との間に画成されて回収熱交換器空気流34bの一部
分を受入れる。図2に示した本発明の実施例では、ハン
ガ46は横断面が概して長方形であり、そして軸方向に
相隔たる環状の前側レール52と後ろ側レール54を含
み、両レールは環状ベース56から半径方向外方に突出
している。ベース56は軸方向に相隔たる1対の従来の
外側フック58を含み、両外側フックは周方向に延在
し、シュラウド42の補完的な内側フック60と従来の
ように結合してシュラウド42をハンガ46に半径方向
に保持する。The shroud support 38 includes an annular hanger 46.
Are located coaxially about the centerline 12, which is also the centerline of the shroud support 38. The hanger 46 is secured to the casing 28 by an integral annular mounting flange 48 that is generally frustoconical. The flange separates the hanger 46 radially inward from the casing 28 within the annular flow passage 50, the annular flow passage 50 being defined between the casing 28 and components radially inwardly spaced therefrom. And receives a portion of the recovered heat exchanger airflow 34b. In the embodiment of the invention shown in FIG. 2, the hanger 46 is generally rectangular in cross-section and includes axially spaced annular front and rear rails 52 and 54, both rails having a radius from an annular base 56. It projects outward in the direction. The base 56 includes a pair of axially spaced conventional outer hooks 58 that extend circumferentially and are conventionally coupled to the complementary inner hooks 60 of the shroud 42 to secure the shroud 42. The hanger 46 is held in the radial direction.
【0015】ハンガ46はまた軸方向に延在する環状頂
部62を含み、この頂部はベース56とほぼ平行に配置
されそれとの間に周方向に延在する流れダクト64を画
成している。流れダクト64は中心線12の周りに同軸
的に配設されている。前側および後ろ側レール52、5
4とベース56は好ましくは互いに一体に形成され、こ
の一体物に頂部62を例えばろう付けにより適当に接合
して密閉流れダクト64を形成しうる。ベース56は複
数の周方向に相隔たる放出孔66を有し、これらの放出
孔は冷却流体68を流れダクト64からシュラウド42
に衝突させるように導いてシュラウドの冷却に役立て
る。Hanger 46 also includes an axially extending annular top 62 which defines a circumferentially extending flow duct 64 disposed generally parallel to base 56. The flow duct 64 is coaxially arranged around the center line 12. Front and rear rails 52, 5
4 and base 56 are preferably integrally formed with one another, to which the top 62 may be suitably joined, for example by brazing, to form a closed flow duct 64. The base 56 has a plurality of circumferentially spaced discharge holes 66 that allow cooling fluid 68 to flow from the duct 64 to the shroud 42.
To help cool the shroud.
【0016】一実施例において、冷却流体68は、圧縮
機14から放出されそして回収熱交換器30内で加熱さ
れる前の圧縮空気流34の一部分である。図1を再度参
照するに、従来の供給導管70が圧縮機14の出口と連
通するように適当に設けられて圧縮空気流34の一部分
を受入れそして圧縮空気流34を冷却流体68としてシ
ュラウド支持体38の近辺でケーシング28を貫通する
ように放出する。再び図2を参照するに、供給導管70
はケーシング28を貫通した状態でそれに従来のように
接合されており、冷却流体68を弧状マニホルド72内
に送り込む。このマニホルドは下流方向に面するマニホ
ルド出口74を有する。製造しかつ試験した一実施例で
は、冷却流体68を単に、取付けフランジ48と、高圧
ノズルをケーシング28に保持する環状取付けフランジ
76との間に通して参考ハンガに導きそれを冷却した。
参考ハンガはハンガ46と実質的に同じであるが、頂部
62を設けてないもので、図3に46bで示してある。
冷却流体は参考ハンガ46bにその全周に沿ってほぼ半
径方向内方に流入しそして参考ハンガ46bを単純な対
流冷却により冷却した。In one embodiment, the cooling fluid 68 is a portion of the compressed air stream 34 prior to being discharged from the compressor 14 and heated in the recovery heat exchanger 30. Referring again to FIG. 1, a conventional feed conduit 70 is suitably provided to communicate with the outlet of compressor 14 to receive a portion of compressed air stream 34 and to use compressed air stream 34 as cooling fluid 68 for the shroud support. Discharge through the casing 28 in the vicinity of 38. Referring again to FIG. 2, the supply conduit 70
Is conventionally joined to the casing 28 through it and directs the cooling fluid 68 into the arcuate manifold 72. The manifold has a downstream facing manifold outlet 74. In one embodiment manufactured and tested, the cooling fluid 68 was simply passed between the mounting flange 48 and an annular mounting flange 76 which held the high pressure nozzle in the casing 28 and directed to a reference hanger to cool it.
The reference hanger is substantially the same as the hanger 46, but without the top 62, and is shown at 46b in FIG.
The cooling fluid entered the reference hanger 46b approximately radially inward along its entire circumference and cooled the reference hanger 46b by simple convection cooling.
【0017】他の参考ハンガ実施例では、やはり図3に
示したU形衝突邪魔板78が考えられ、この場合、冷却
空気68は衝突邪魔板78を通るように半径方向内方に
導かれてハンガ46bの衝突冷却に用いられた。In another reference hanger embodiment, a U-shaped impingement baffle 78, also shown in FIG. 3, is contemplated, in which case cooling air 68 is directed radially inward through impingement baffle 78. It was used for collision cooling of the hanger 46b.
【0018】図4は時間に対する半径方向膨張を例示す
るグラフで、第1時点T1 から第2時点T2 までの低出
力から高出力に至るバースト状態における過渡応答の一
例について翼端44bで測定した半径方向膨張をロータ
曲線80で示す。図3に示した参考ハンガ46bに衝突
邪魔板78を設けない場合にシュラウド42の内面で測
定した対応半径方向膨張を図4に破線の参考シュラウド
曲線82で示す。この半径方向膨張は、主として、シュ
ラウドを支持するハンガの熱変位によるものである。シ
ュラウド42と翼端44bとの間の最小半径方向間隙C
1 の狭点(pinch point)が狭点時点Tp に示されてい
る。狭点間隙C1 がエンジン10のこの実施例で発生す
るのは、ロータの動翼44がシュラウド42より速く膨
張するからであり、動翼44のロータ時定数τr はシュ
ラウド支持体38のシュラウド支持体時定数τs より少
ない。換言すると、シュラウド支持体38は動翼44に
比べて熱応答が遅い。FIG. 4 is a graph illustrating the radial expansion with respect to time. An example of the transient response in a burst state from low power to high power from the first time point T 1 to the second time point T 2 was measured at the tip 44b. The radial expansion done is shown by the rotor curve 80. The corresponding radial expansion measured on the inner surface of the shroud 42 when the reference hanger 46b shown in FIG. 3 is not provided with the collision baffle 78 is shown in FIG. 4 by the dashed reference shroud curve 82. This radial expansion is primarily due to the thermal displacement of the hangers that support the shroud. Minimum radial clearance C between shroud 42 and tip 44b
A pinch point of 1 is shown at the narrow point time point T p . The narrow point clearance C 1 occurs in this embodiment of the engine 10 because the rotor blades 44 expand faster than the shroud 42, and the rotor time constant τ r of the rotor 44 is the shroud support 38 shroud. Less than the support time constant τ s . In other words, shroud support 38 has a slower thermal response than blade 44.
【0019】熱時定数τは次式で表すことができる。The thermal time constant τ can be expressed by the following equation.
【0020】τ=mCp /(hA) ただし、mは冷却されているシュラウド支持体の質量
で、例えば、冷却中のハンガ46の質量で表されうるも
のであり、Cp は冷却流体または空気68の比熱であ
り、Aは冷却流体68を受ける面積、例えば、前側およ
び後ろ側レール52、54とベース56の内面の面積で
あり、hは熱伝達率である。時定数τは、例えば、過渡
状態発生開始から翼端44bとシュラウド42の新しい
定常状態半径方向位置の約62%に達するまでに要する
時間を表す。Τ = mC p / (hA) where m is the mass of the shroud support being cooled, which can be represented, for example, by the mass of the hanger 46 during cooling, and C p is the cooling fluid or air. Is the specific heat of 68, A is the area receiving the cooling fluid 68, for example, the area of the inner surfaces of the front and rear rails 52, 54 and the base 56, and h is the heat transfer coefficient. The time constant τ represents, for example, the time required from the start of the transient state to reach about 62% of the new steady state radial position of the blade tip 44b and shroud 42.
【0021】本発明の一目的によれば、翼端44bと、
ハンガ46により支持されたシュラウド42とにおける
熱膨張応答の整合の改良が望まれ、これはシュラウド支
持体38の時定数τs を動翼44の時定数τr に対して
減らすことにより達成されうる。邪魔板78からの衝突
冷却の場合の熱伝達率hは従来約1000BTU/(hr ・ft
2 ・゜F)程度であり、これが時定数に与える影響は、mと
Cp とAによる小さな影響に比べてかなり大きい。従っ
て、時定数τs はmとAの値の実際の変化にはほとんど
影響されないが、熱伝達率hの変化には過度に敏感であ
る。そして、定常状態運転と過渡運転の両方に対する設
計は衝突冷却の場合いっそう困難である。According to one object of the present invention, a wing tip 44b,
An improved match of the thermal expansion response with the shroud 42 supported by the hangers 46 is desired, which can be achieved by reducing the time constant τ s of the shroud support 38 relative to the time constant τ r of the blade 44. . The heat transfer coefficient h in the case of collision cooling from the baffle plate 78 is about 1000 BTU / (hr.ft
2 ° F.), which has a much larger effect on the time constant than the small effects of m, C p and A. Therefore, the time constant τ s is hardly affected by the actual changes in the values of m and A, but is overly sensitive to changes in the heat transfer coefficient h. And designing for both steady state and transient operation is more difficult with impingement cooling.
【0022】冷却流体68を図3に示した参考ハンガ4
6b内に半径方向に導入することによって得られる熱伝
達率hは、邪魔板78がない場合、約4〜8BTU/(hr ・
ft2 ・゜F)であり、その結果、図4に示した参考シュラウ
ド曲線82が得られた。しかし、シュラウド42と動翼
44との時定数の差により、過渡運転中依然として比較
的小さな翼端間隙狭点が生じる。また、前側および後ろ
側レール52、54の温度に比較的大きな周方向変化が
観察された。これは導入された回収熱交換器空気流34
bの影響によるものである。The reference hanger 4 shown in FIG.
The heat transfer coefficient h obtained by introducing radially into 6b is about 4 to 8 BTU / (hr.
ft 2 · ° F), and as a result, the reference shroud curve 82 shown in FIG. 4 was obtained. However, due to the time constant difference between shroud 42 and blade 44, a relatively small tip clearance narrowing occurs during transient operation. In addition, a relatively large circumferential change was observed in the temperature of the front and rear rails 52, 54. This is due to the introduction of the recovered heat exchanger air stream 34
This is due to the influence of b.
【0023】本発明の一目的によれば、図2に示したハ
ンガ46は頂部62を含むことが好ましく、これにより
密閉流れダクト64が形成され冷却流体68を従来周知
の管流として通しうる。頂部の開いた参考ハンガ46b
の衝突冷却および対流冷却されるものはいずれも望まし
くないとして使用されず、前者の場合の熱伝達率hより
小さくそして後者の場合のそれより大きい熱伝達率hを
用いることにより、ハンガ46によるシュラウド42の
時定数τs をより正確に制御してシュラウド42と翼端
44bとの間の熱応答をより良く整合しうる。In accordance with one object of the present invention, the hanger 46 shown in FIG. 2 preferably includes a top portion 62 which forms a closed flow duct 64 through which the cooling fluid 68 can pass as a well known tube flow. Reference hanger 46b with the top open
Both the impingement-cooled and convection-cooled, which are undesired, are not used and by using a heat transfer coefficient h that is less than the heat transfer coefficient h in the former case and greater than that in the latter case, the shroud by the hanger 46 is The time constant τ s of 42 may be more precisely controlled to better match the thermal response between shroud 42 and tip 44b.
【0024】ハンガ46を図2に示すように頂部62で
密閉することにより、また、冷却流体68をハンガ流れ
ダクト64内で周方向に導いてハンガ46を冷却する手
段84を設けることにより、周知の管流が流れダクト6
4内に発生しそして本発明により有効に用いられてハン
ガ46と動翼44との時定数をより良く整合し、過渡応
答中翼端間隙狭点をより良く制御、例えば、増大する等
の利点をもたらす。2 by sealing the hanger 46 at the top 62 as shown in FIG. 2 and by providing means 84 for circumferentially guiding the cooling fluid 68 within the hanger flow duct 64 to cool the hanger 46. Pipe flow of the duct 6
4 and used effectively in accordance with the present invention to better match the time constants of the hanger 46 and the blade 44, and to better control, eg, increase, the tip clearance narrow point during transient response. Bring
【0025】さらに詳述すると、本発明の一実施例によ
れば、冷却手段84は図2と図5と図6に例示したよう
に、複数の周方向に相隔たる冷却流体出口86、例え
ば、第1、第2、第3および第4流体出口86a、86
b、86c、86dを含み、これらの流体出口はハンガ
ダクト64内に適切に配置され、全てが一方の周方向
(図6に示すように時計方向)だけに面して冷却流体6
8をダクト64内で周方向に放出して単一方向の管流を
発生し、この管流に関するハンガ46の時定数τs は動
翼44の時定数τr とより良く整合するように減らされ
得る。製造されかつ試験されたハンガ46の一実施例で
あって冷却手段84を含むものでは、図4に示したよう
な改良シュラウド曲線88が得られ、これはロータ曲線
80とより良く整合し、そして同じ狭点時点Tp での翼
端間隙狭点C2 が拡大している。ハンガ46による時定
数τs は、図4に示したシュラウド曲線88とロータ曲
線80との間のより均等な間隔によって示されるよう
に、動翼44の時定数τr とより良く整合する。More specifically, in accordance with one embodiment of the present invention, the cooling means 84 includes a plurality of circumferentially spaced cooling fluid outlets 86, eg, as illustrated in FIGS. First, second, third and fourth fluid outlets 86a, 86
b, 86c, 86d, these fluid outlets are suitably arranged in the hanger duct 64, all facing only one circumferential direction (clockwise as shown in FIG. 6).
8 is discharged circumferentially in the duct 64 to produce a unidirectional tube flow, the time constant τ s of the hanger 46 for this tube flow is reduced to better match the time constant τ r of the blade 44. Can be done. One embodiment of the hanger 46 that has been manufactured and tested and that includes the cooling means 84 results in an improved shroud curve 88 as shown in FIG. 4, which better matches the rotor curve 80, and The blade tip clearance narrow point C 2 at the same narrow point time point T p is expanded. The time constant τ s by the hanger 46 better matches the time constant τ r of the blade 44, as shown by the more uniform spacing between the shroud curve 88 and the rotor curve 80 shown in FIG.
【0026】図5と図6を再び参照するに、流体出口8
6は簡単なオリフィスでよく、好ましくは等間隔で相隔
たり、例えば、中心線12から共通半径の所で等角度で
相隔たり、流れダクト64内の冷却流体68の周方向速
度を概して均等にする。一つ以上の流体出口86を用い
得るが、少なくとも2つの流体出口86が好適であり、
両出口は約180度隔てられて流体68の速度分布をほ
ぼ均等にする。というのは、流体68は出口86の一つ
から流れダクト64を経て他の出口86まで流れるから
である。もちろん、もっと多くの出口86を流れダクト
64内に設ければ、流体68の周方向速度はそれだけ均
等になる。なぜなら、それに応じて、一つの出口86か
ら次の出口86までの流体68の質量流量が少なくなる
からである。Referring again to FIGS. 5 and 6, the fluid outlet 8
6 may be simple orifices, preferably equidistantly spaced, eg equiangularly spaced from the centerline 12 at a common radius, to generally equalize the circumferential velocity of the cooling fluid 68 in the flow duct 64. . Although more than one fluid outlet 86 may be used, at least two fluid outlets 86 are preferred,
The two outlets are separated by about 180 degrees to make the velocity distribution of the fluid 68 substantially uniform. The fluid 68 flows from one of the outlets 86 through the flow duct 64 to the other outlet 86. Of course, the more outlets 86 provided in the flow duct 64, the more evenly the circumferential velocity of the fluid 68 will be. This is because the mass flow rate of the fluid 68 from one outlet 86 to the next outlet 86 is correspondingly reduced.
【0027】従来知られているように、時定数τは熱伝
達率hに反比例しそして熱伝達率hは冷却流体68の速
度に正比例するので、出口86の周方向配置は、ハンガ
46近辺に導かれる回収熱交換器空気流34bの周方向
に沿って変わる温度によるハンガ46の環境温度の周方
向変化に応じてハンガ46の様々な冷却度をもたらすよ
うに予め選定されうる。さらに、冷却流体68を、図3
に示した参考ハンガ46bの具体例で生じるように流れ
ダクト64の全周に沿って半径方向に流れダクト64内
に導入する代りに、流れダクト64内で周方向に導くこ
とにより、比較的大きな熱伝達率hが得られる。As is known in the art, the time constant τ is inversely proportional to the heat transfer coefficient h, and the heat transfer coefficient h is directly proportional to the speed of the cooling fluid 68. Therefore, the circumferential arrangement of the outlet 86 is close to the hanger 46. It may be preselected to provide different degrees of cooling of the hanger 46 in response to circumferential changes in the ambient temperature of the hanger 46 due to the circumferentially varying temperature of the guided recovery heat exchanger airflow 34b. Further, cooling fluid 68 is added to FIG.
Instead of being introduced radially into the flow duct 64 along the entire circumference of the flow duct 64 as occurs in the embodiment of the reference hanger 46b shown in FIG. The heat transfer coefficient h is obtained.
【0028】例えば、図2に示したハンガ46の熱伝達
解析によれば、熱伝達率hは約40BTU/(hr ・ ft2 ・゜F)
と推定され、これに比べ、図3に示した参考ハンガ46
bに衝突邪魔板78を用いない場合の熱伝達率hは約4
〜8BTU/(hr ・ ft2 ・゜F)程の小さな値となる。改善され
た熱伝達率hは、ハンガ46による時定数τs をかなり
減らして動翼44の時定数τr とより良く整合しそして
ハンガ46の温度の周方向変化を減らすのに有効であ
り、従って、翼端間隙Cの周方向変化を効果的に減ら
す。For example, according to the heat transfer analysis of the hanger 46 shown in FIG. 2, the heat transfer coefficient h is about 40 BTU / (hr · ft 2 · ° F).
It is estimated that the reference hanger 46 shown in FIG.
When the collision baffle 78 is not used for b, the heat transfer coefficient h is about 4
The value is as small as ~ 8BTU / (hr · ft 2 · ° F). The improved heat transfer coefficient h is effective in significantly reducing the time constant τ s by the hanger 46 to better match the time constant τ r of the blade 44 and in reducing circumferential changes in the temperature of the hanger 46. Therefore, the change in the blade tip clearance C in the circumferential direction is effectively reduced.
【0029】4つの流体出口86の各々に冷却流体を送
給するために、冷却手段84は、図2と図5と図6に示
したように、対応する複数のの出口管90、例えば、第
1、第2、第3および第4出口管90a、90b、90
c、90dをさらに含む。これらの出口管90はそれぞ
れの流体出口86を含み、出口86はハンガダクト64
内のそれぞれの出口管のさもなくば閉ざされている末端
に設けられ、全出口が同じ周方向に面している。出口管
90は、好ましくは、流れダクト64内からほぼ軸方向
に後方に延在し、後ろ側レール54を貫通し、次いでそ
れぞれ湾曲して取付けフランジ48の筒形部48bに沿
いかつ中心線12の周りに同軸的に周方向に延びるよう
に形成される。To deliver cooling fluid to each of the four fluid outlets 86, the cooling means 84 includes a plurality of corresponding outlet tubes 90, eg, as shown in FIGS. 2, 5 and 6. First, second, third and fourth outlet tubes 90a, 90b, 90
c, 90d are further included. These outlet tubes 90 include respective fluid outlets 86, the outlets 86 being the hanger ducts 64.
Provided at the otherwise closed ends of the respective outlet pipes therein, all outlets face the same circumferential direction. Outlet tubes 90 preferably extend generally axially rearward from within flow duct 64, extend through rear rail 54, and then are each curved along tubular portion 48b of mounting flange 48 and along centerline 12. Is formed so as to extend coaxially around the circumference in the circumferential direction.
【0030】冷却手段84は複数の供給管92、例え
ば、第1および第2供給管92a、92bをさらに含
み、各供給管はそれに対応する1対の出口管90に冷却
流体68を導くように作用する。図6と図7に示すよう
に、両供給管92はそれぞれの入口94a、94bを有
し、両入口は隣合って配置され共通マニホルド72の出
口74と連通してそれから冷却流体68を受入れる。両
供給管92はそれぞれの出口96a、96bを有し、各
出口は対応する管90の近接端にある1対の入口98と
連通するように配置されている。すなわち、第1および
第2出口管入口98a、98bが第1供給管出口96a
に接続され、そして第3および第4出口管入口98c、
98dが第2供給管出口96bに接続されている。各供
給管92は、好ましくは、それに対応する出口管90か
らほぼ半径方向外方に延在して取付けフランジ筒形部4
8bを貫通し、次いで中心線12の周りにほぼ同軸的に
周方向にある円弧距離だけ延び、さらに隣の供給管92
の対応部分近くで半径方向上方に曲がって供給管入口9
4a、94bに至りそこでマニホルド72と連通するよ
うに形成される。The cooling means 84 further includes a plurality of supply tubes 92, eg, first and second supply tubes 92a, 92b, each supply tube directing the cooling fluid 68 to a corresponding pair of outlet tubes 90. To work. As shown in FIGS. 6 and 7, both supply pipes 92 have respective inlets 94a, 94b, which are arranged next to each other and communicate with the outlet 74 of the common manifold 72 to receive the cooling fluid 68 therefrom. Both supply pipes 92 have respective outlets 96a, 96b, each outlet arranged to communicate with a pair of inlets 98 at the proximal ends of the corresponding pipes 90. That is, the first and second outlet pipe inlets 98a and 98b are the first supply pipe outlet 96a.
And third and fourth outlet pipe inlets 98c,
98d is connected to the second supply pipe outlet 96b. Each supply tube 92 preferably extends generally radially outwardly from its corresponding outlet tube 90 to provide a mounting flange tubular section 4.
8b, and then extends approximately coaxially about the centerline 12 for an arc distance in the circumferential direction, and further adjoins the supply pipe 92.
Bent upwards in the radial direction near the corresponding part of the supply pipe inlet 9
4a, 94b, where they are formed so as to communicate with the manifold 72.
【0031】出口管90と供給管92の上述の形状は、
冷却流体68を共通マニホルド72から4つの周方向に
相隔たる流体出口86に導くのに好適である。管90、
92は、第1に、冷却流体68を流れダクト64に導く
いっそう直接的な通路として、回収熱交換器空気流34
bによる冷却流体68の間接加熱を減らすのに好適であ
る。こうして、比較的低温の圧縮空気流34を冷却流体
68として流れダクト64に供給することができ、その
際、冷却流体の経路に沿う吸熱による温度上昇は比較的
わずかであり、また冷却流体68のハンガ46への流れ
からの漏れは発生しない。The above-described shapes of the outlet pipe 90 and the supply pipe 92 are as follows.
It is suitable to direct the cooling fluid 68 from the common manifold 72 to four circumferentially spaced fluid outlets 86. Tube 90,
92 firstly serves as a more direct passage for the cooling fluid 68 to the flow duct 64 and serves as a recovery heat exchanger air stream 34.
It is suitable for reducing indirect heating of the cooling fluid 68 by b. In this way, the relatively cool compressed air stream 34 can be supplied to the flow duct 64 as the cooling fluid 68, the temperature rise due to the heat absorption along the path of the cooling fluid being relatively small, and of the cooling fluid 68. No leakage from the flow to the hanger 46 occurs.
【0032】さらに、冷却流体68を4つの流体出口8
6の各々において所定温度で供給することも望ましく、
各出口の流体温度は本発明の一実施例によれば実質的に
均等である。従って、マニホルド72における供給管入
口94a、94bからそれぞれの供給管92と出口管9
0を経て4つの流体出口86に達する4つの流路がそれ
ぞれ流路長、すなわち、第1、第2、第3、第4流路長
L1 、L2 、L3 、L4 を有しそしてこれらの流路長は
ほぼ相等しいことが好ましい。Further, the cooling fluid 68 is supplied to the four fluid outlets 8
It is also desirable to supply at a predetermined temperature in each of 6,
The fluid temperature at each outlet is substantially equal, according to one embodiment of the invention. Therefore, from the supply pipe inlets 94a and 94b in the manifold 72, the respective supply pipes 92 and outlet pipes 9 are provided.
Each of the four flow paths reaching the four fluid outlets 86 via 0 has a flow path length, that is, a first, a second, a third, and a fourth flow path length L 1 , L 2 , L 3 , L 4 . And it is preferable that these flow path lengths are substantially the same.
【0033】図7は冷却流体68を入口94a、94b
からそれぞれの流体出口86a、86b、86c、86
dに導く供給管92と出口管90の概略を示す。4つの
流路長L1 、L2 、L3 、L4 も示してある。供給管9
2と出口管90は、この実施例では、4つの出口86か
ら出る冷却流体68の温度をほぼ均等にするような所定
の寸法と形状を有する。出口管90と供給管92は、
(図2に示したように)流路50内に配置されるので、
回収熱交換器空気流34bにより加熱される。しかし、
管90、92はフランジ76により保護されており回収
熱交換器空気流34bに直接露出されない。また、実質
的に等しい流路長L1 〜L4 を設けることにより、管9
0、92を通る冷却流体68の吸熱量はほぼ等しいの
で、冷却流体68は共通温度で出口86から放出され
る。従って、ダクト64を通る冷却流体68によるハン
ガ46の熱膨縮は比較的均等であり、周方向のひずみと
それに伴う翼端間隙Cの周方向変化を減らし得る。In FIG. 7, the cooling fluid 68 is introduced into the inlets 94a and 94b.
From the respective fluid outlets 86a, 86b, 86c, 86
The outline of the supply pipe 92 and the outlet pipe 90 leading to d is shown. Also shown are four flow path lengths L 1 , L 2 , L 3 , L 4 . Supply pipe 9
2 and the outlet tube 90 are of a predetermined size and shape in this embodiment to approximately equalize the temperature of the cooling fluid 68 exiting the four outlets 86. The outlet pipe 90 and the supply pipe 92 are
Since it is located in the channel 50 (as shown in FIG. 2),
It is heated by the recovery heat exchanger airflow 34b. But,
The tubes 90, 92 are protected by the flange 76 and are not directly exposed to the recovered heat exchanger airflow 34b. Further, by providing the substantially equal flow path lengths L 1 to L 4 , the pipe 9
The heat absorptions of the cooling fluid 68 passing through 0 and 92 are almost equal, so that the cooling fluid 68 is discharged from the outlet 86 at a common temperature. Therefore, the thermal expansion and contraction of the hanger 46 by the cooling fluid 68 passing through the duct 64 is relatively uniform, and it is possible to reduce the circumferential strain and the accompanying circumferential change in the blade tip clearance C.
【0034】図7に概略的に示すように、この実施例に
おいて等しい流路長L1 〜L4 を得るために、4つの流
体出口86は約90度ずつ周方向に相隔たっており、ま
た供給管出口96a、96bは好ましくは約180度相
隔たっておりそして流体出口86のうちの対応出口間に
約45度の間隔で配置されている。さらに、第1および
第2供給管入口94a、94bは第1および第2供給管
出口96a、96bそれぞれから周方向に約90度隔た
っている。また第1および第2出口管90a、90b
は、好ましくは、第3および第4出口管90c、90d
と対向するようにそれらから周方向に隔てられる。そう
すると、第1および第2供給管92a、92bと、それ
ぞれに接続された出口管は互いに重なり合わない。As shown schematically in FIG. 7, in order to obtain equal flow path lengths L 1 -L 4 in this embodiment, the four fluid outlets 86 are circumferentially spaced by about 90 degrees and are also fed. The tube outlets 96a, 96b are preferably about 180 degrees apart and are spaced about 45 degrees apart between corresponding ones of the fluid outlets 86. Further, the first and second supply pipe inlets 94a, 94b are circumferentially separated from the first and second supply pipe outlets 96a, 96b by about 90 degrees. Also, the first and second outlet pipes 90a, 90b
Are preferably third and fourth outlet tubes 90c, 90d.
Circumferentially separated from them so as to face. Then, the first and second supply pipes 92a and 92b and the outlet pipes connected to each other do not overlap each other.
【0035】さらに、出口管90と供給管92の諸部を
中心線12の周りに周方向に配置することにより管の熱
膨縮に対処し、管に誘起される熱応力を減らし得る。熱
膨縮による出口管90の熱応力をさらに減らすために、
各出口管90は好ましくはほぼU形の段部100を含
み、この段部は取付けフランジ筒形部48b近辺の出口
管の周方向延在部分において軸方向に張り出している。
段部100は図6と図8に示され、図8はシュラウド支
持体38から除去した出口管90と供給管92の斜視図
である。Further, by arranging parts of the outlet pipe 90 and the supply pipe 92 in the circumferential direction around the center line 12, it is possible to cope with thermal expansion and contraction of the pipe and reduce thermal stress induced in the pipe. In order to further reduce the thermal stress of the outlet pipe 90 due to thermal expansion and contraction,
Each outlet tube 90 preferably includes a generally U-shaped step 100 that extends axially in the circumferentially extending portion of the outlet tube near the mounting flange tubular portion 48b.
Step 100 is shown in FIGS. 6 and 8, which is a perspective view of outlet tube 90 and supply tube 92 removed from shroud support 38.
【0036】従って、上述の改良されたタービンシュラ
ウド支持体38は、動翼44の半径方向移動に関する時
定数をハンガ46によるシュラウド42の半径方向移動
に関する時定数とより良く整合するように作用しそして
過渡運転中翼端間隙狭点を効率的に拡大する。さらに、
ハンガ46の温度の周方向変化も減らされてハンガ46
の真円度が高まり、そして翼端間隙Cの対応周方向変化
が減少する。また、本発明によるシュラウド支持体38
による改良された冷却効果は、前側および後ろ側レール
52、54間の温度差の低減に有効であり、これも、前
側と後ろ側のレール52、54間の半径方向移動差によ
る翼端間隙Cの対応変化を減らす。Accordingly, the improved turbine shroud support 38 described above acts to better match the time constant for radial movement of the blade 44 with the time constant for radial movement of the shroud 42 by the hanger 46, and Efficiently expand the tip clearance narrow point during transient operation. further,
Circumferential changes in the temperature of the hanger 46 are also reduced, and the hanger 46
Roundness increases, and the corresponding circumferential change in blade tip clearance C decreases. Also, the shroud support 38 according to the present invention.
The improved cooling effect due to is effective in reducing the temperature difference between the front and rear rails 52 and 54, which is also due to the difference in the radial tip between the front and rear rails 52 and 54 in the blade tip clearance C. Correspondence of change is reduced.
【0037】以上、本発明の好適実施例と考えられるも
のを説明したが、もちろん、様々な改変が本発明の範囲
内で可能である。While what has been considered to be the preferred embodiments of the invention has been described above, of course, various modifications are possible within the scope of the invention.
【図1】本発明の一実施例によるタービンシュラウド支
持体を含む回収熱交換器付きガスタービンエンジンの一
例の概略縦断面図である。FIG. 1 is a schematic vertical cross-sectional view of an example of a gas turbine engine with a recovery heat exchanger including a turbine shroud support according to an embodiment of the present invention.
【図2】本発明の一実施例による図1に示したエンジン
用のタービンシュラウド支持体の拡大縦断面図である。2 is an enlarged vertical cross-sectional view of a turbine shroud support for the engine shown in FIG. 1 according to one embodiment of the present invention.
【図3】参考例としてのシュラウド支持体の密閉されて
いないハンガと比較して、図2に示したシュラウド支持
体ハンガの一部を仮想線で示す斜視図である。FIG. 3 is a perspective view showing a part of the shroud support hanger shown in FIG. 2 in phantom lines, as compared to an unsealed hanger of the shroud support as a reference example.
【図4】ロータに対する図2に示したシュラウド支持体
と参考シュラウド支持体の時間に対する半径方向膨張を
示すグラフである。4 is a graph showing radial expansion of the shroud support shown in FIG. 2 and a reference shroud support shown in FIG. 2 for a rotor.
【図5】図2に示したシュラウド支持体の線5ー5に沿
う上流向き横断面図である。FIG. 5 is an upstream cross-sectional view of the shroud support shown in FIG. 2 taken along line 5-5.
【図6】図2に示したシュラウド支持体を部分的に仮想
線で示す後ろ向き斜視図である。FIG. 6 is a rear perspective view of the shroud support shown in FIG. 2 partially shown in phantom.
【図7】図2に示したシュラウド支持体の横断面図で、
出口管と供給管の相対位置の概略を示す。7 is a cross-sectional view of the shroud support shown in FIG.
The outline of the relative position of an outlet pipe and a supply pipe is shown.
【図8】図7に示した出口管と供給管の概略斜視図であ
る。8 is a schematic perspective view of an outlet pipe and a supply pipe shown in FIG.
28 ケーシング 38 シュラウド支持体 42 タービンシュラウド 44 タービン動翼 46 ハンガ 52、54 レール 56 ベース 62 環状頂部 64 ダクト 66 放出孔 72 マニホルド 86、86a、86b、86c、86d 冷却流体出口 90、90a、90b、90c、90d 出口管 92、92a、92b 供給管 98、98a、98b、98c、98d 出口管入口 100 U形段部 28 Casing 38 Shroud support 42 Turbine shroud 44 Turbine blade 46 Hanger 52, 54 Rail 56 Base 62 Annular top 64 Duct 66 Discharge hole 72 Manifold 86, 86a, 86b, 86c, 86d Cooling fluid outlet 90, 90a, 90b, 90c , 90d outlet pipe 92, 92a, 92b supply pipe 98, 98a, 98b, 98c, 98d outlet pipe inlet 100 U-shaped step
Claims (13)
であって、 環状ケーシングと、 このケーシングに固定されそれから半径方向内方に離隔
してそれとの間に環状流路を画成するもので、前記中心
線の周りに同軸的に配置され、そして複数の周方向に相
隔たるタービン動翼の半径方向上側に配置し得るシュラ
ウドを半径方向に支持するベースと、前記ベ―スから前
記環状流路に向って半径方向外側に延在し、かつ周方向
に延在する流れダクトとを有する、環状ハンガと、 一方の周方向への流れを得るために 冷却流体を前記ハン
ガダクト内で周方向に導くことにより前記ハンガを冷却
する手段とからなるシュラウド支持体。1. A shroud support having a longitudinal centerline, comprising: an annular casing fixed to the casing and spaced radially inwardly therefrom to define an annular flow path therebetween. Coaxially arranged around the center line and arranged in a plurality of circumferential directions
Shuras that can be placed radially above the separating turbine blades
The base that supports the wood in the radial direction and the front of the base.
Circumferentially, extending radially outward toward the annular flow path
A shroud support comprising an annular hanger having a flow duct extending into the hanger, and means for cooling the hanger by circumferentially guiding a cooling fluid in the hanger duct to obtain one circumferential flow. .
ト内に配置されそして一方の周方向に面して前記冷却流
体を前記ダクト内で周方向に放出する複数の周方向に相
隔たる冷却流体出口を含む、請求項1記載のシュラウド
支持体。2. The hanger cooling means includes a plurality of circumferentially spaced cooling fluid outlets disposed in the hanger duct and facing one circumferential direction for discharging the cooling fluid circumferentially in the duct. The shroud support of claim 1, comprising:
請求項2記載のシュラウド支持体。3. The shroud support of claim 2, wherein the fluid outlets are equidistantly spaced.
らに含み、これらの出口管はそれぞれ前記ハンガダクト
内のそれぞれの末端に設けた前記流体出口を有し、前記
出口管は前記複数の流体出口から放出し得る前記冷却流
体の温度を実質的に均等にするような所定の寸法と形状
を有する、請求項2記載のシュラウド支持体。4. The hanger cooling means further includes a plurality of outlet pipes, each of the outlet pipes having the fluid outlet provided at a respective end of the hanger duct, the outlet pipe having the plurality of fluid outlets. The shroud support of claim 2, having a predetermined size and shape to substantially equalize the temperature of the cooling fluid that can be discharged from the shroud support.
らに含み、各供給管は前記冷却流体を前記出口管の対応
する1対に導き、前記供給管は前記複数の流体出口から
放出し得る前記冷却流体の温度を実質的に均等にするよ
うに前記出口管とともに所定の寸法と形状を有する、請
求項4記載のシュラウド支持体。5. The hanger cooling means further comprises a plurality of supply pipes, each supply pipe directing the cooling fluid to a corresponding pair of outlet pipes, the supply pipes being capable of discharging from the plurality of fluid outlets. The shroud support of claim 4, having a predetermined size and shape with the outlet tube to substantially equalize the temperature of the cooling fluid.
れの出口管と、2本の前記供給管とを備え、各供給管は
前記冷却流体を受入れる入口を有し、前記2本の供給管
入口からそれぞれの供給管と出口管を経て前記4つの流
体出口に達する4つの流路の各々が流路長を有し、これ
らの4つの流路長はほぼ相等しい、請求項5記載のシュ
ラウド支持体。6. Four fluid outlets and four respective outlet tubes and two said supply tubes, each supply tube having an inlet for receiving said cooling fluid, said two supply tubes. The shroud of claim 5, wherein each of the four flow passages from the inlet to the four fluid outlets through respective feed and outlet pipes has a flow passage length, the four passage lengths being substantially equal. Support.
ており、 前記出口管の第1および第2管が前記中心線の周りにほ
ぼ同軸的に延在し、そして前記供給管の第1管の出口に
接続した入口を有し、 前記出口管の第3および第4管が前記中心線の周りにほ
ぼ同軸的に延在し、そして前記供給管の第2管の出口に
接続した入口を有し、また 前記第1および第2出口管は前記第3および第4出口管
と対向するようにそれらから周方向に隔たっている、請
求項6記載のシュラウド支持体。7. The four fluid outlets are equally spaced apart, the first and second tubes of the outlet tube extending substantially coaxially about the centerline, and the first of the supply tubes. An inlet having an inlet connected to an outlet of a tube, the third and fourth tubes of the outlet tube extending substantially coaxially about the centerline and connected to an outlet of a second tube of the supply tube 7. The shroud support according to claim 6, further comprising: and first and second outlet tubes circumferentially spaced from and opposite the third and fourth outlet tubes.
の周りにほぼ同軸的に延在し、そして両供給管の前記入
口は共通マニホルドから前記冷却流体を受入れるように
隣合っている、請求項7記載のシュラウド支持体。8. The first and second supply pipes extend substantially coaxially about the centerline, and the inlets of both supply pipes are adjacent to receive the cooling fluid from a common manifold. The shroud support according to claim 7.
向に相隔たっており、 前記第1および第2供給管出口
は約180度相隔たっておりそして前記流体出口のうち
の対応出口間に約45度の間隔で配置されており、また
前記第1および第2供給管入口は前記第1および第2供
給管出口それぞれから約90度隔たっている、請求項8
記載のシュラウド支持体。9. The four fluid outlets are circumferentially spaced by about 90 degrees, the first and second supply pipe outlets are spaced about 180 degrees, and between the corresponding ones of the fluid outlets. 9. 45 degrees apart, and said first and second feed tube inlets are spaced about 90 degrees from each of said first and second feed tube outlets.
The shroud support described.
あり、そして軸方向に相隔たりかつ前記ベースから半径
方向外方に延在する前側および後ろ側レールと、前記ベ
ースとほぼ平行に配置されてそれとの間に前記流れダク
トを画成する軸方向延在頂部とを含む、請求項9記載の
シュラウド支持体。10. The hanger is generally rectangular in cross-section and is positioned substantially parallel to the base with front and rear rails axially spaced apart and extending radially outward from the base. 10. The shroud support of claim 9 including an axially extending apex therebetween defining the flow duct.
クトから前記シュラウドに衝突させるように導く複数の
周方向に相隔たる放出孔を有する、請求項10記載のシ
ュラウド支持体。11. The shroud support of claim 10, wherein the base has a plurality of circumferentially spaced discharge holes that guide the fluid from the flow duct to impinge on the shroud.
る段部を有する、請求項9記載のシュラウド支持体。12. The shroud support according to claim 9, wherein each outlet pipe has a step portion that allows thermal displacement of the outlet pipe.
あり、そして軸方向に相隔たりかつ前記ベースから半径
方向外方に延在する前側および後ろ側レールと、前記ベ
ースとほぼ平行に配置されてそれとの間に前記流れダク
トを画成する軸方向延在頂部とを含む、請求項2記載の
シュラウド支持体。13. The hanger is generally rectangular in cross-section and is positioned substantially parallel to the base with front and rear rails axially spaced apart and extending radially outward from the base. The shroud support of claim 2 including an axially extending apex therebetween defining the flow duct.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US666,959 | 1991-03-11 | ||
US07/666,959 US5167487A (en) | 1991-03-11 | 1991-03-11 | Cooled shroud support |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH04303104A JPH04303104A (en) | 1992-10-27 |
JPH0751888B2 true JPH0751888B2 (en) | 1995-06-05 |
Family
ID=24676243
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP4019345A Expired - Fee Related JPH0751888B2 (en) | 1991-03-11 | 1992-01-09 | Cooling shroud support |
Country Status (6)
Country | Link |
---|---|
US (1) | US5167487A (en) |
EP (1) | EP0503752B1 (en) |
JP (1) | JPH0751888B2 (en) |
CA (1) | CA2061939C (en) |
DE (1) | DE69210077T2 (en) |
IL (1) | IL100515A0 (en) |
Families Citing this family (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5927942A (en) * | 1993-10-27 | 1999-07-27 | United Technologies Corporation | Mounting and sealing arrangement for a turbine shroud segment |
US5380150A (en) * | 1993-11-08 | 1995-01-10 | United Technologies Corporation | Turbine shroud segment |
US5540547A (en) * | 1994-06-23 | 1996-07-30 | General Electric Company | Method and apparatus for damping vibrations of external tubing of a gas turbine engine |
US5639210A (en) * | 1995-10-23 | 1997-06-17 | United Technologies Corporation | Rotor blade outer tip seal apparatus |
US5813830A (en) * | 1996-02-09 | 1998-09-29 | Allison Engine Company, Inc. | Carbon seal contaminant barrier system |
DE29714742U1 (en) * | 1997-08-18 | 1998-12-17 | Siemens AG, 80333 München | Heat shield component with cooling fluid return and heat shield arrangement for a hot gas-carrying component |
US6139257A (en) * | 1998-03-23 | 2000-10-31 | General Electric Company | Shroud cooling assembly for gas turbine engine |
US6626635B1 (en) * | 1998-09-30 | 2003-09-30 | General Electric Company | System for controlling clearance between blade tips and a surrounding casing in rotating machinery |
US6902371B2 (en) * | 2002-07-26 | 2005-06-07 | General Electric Company | Internal low pressure turbine case cooling |
DE10352089A1 (en) * | 2003-11-07 | 2005-06-09 | Alstom Technology Ltd | Method for operating a turbomachine, and turbomachinery |
US7147432B2 (en) * | 2003-11-24 | 2006-12-12 | General Electric Company | Turbine shroud asymmetrical cooling elements |
US6997673B2 (en) * | 2003-12-11 | 2006-02-14 | Honeywell International, Inc. | Gas turbine high temperature turbine blade outer air seal assembly |
US7588412B2 (en) * | 2005-07-28 | 2009-09-15 | General Electric Company | Cooled shroud assembly and method of cooling a shroud |
US7771160B2 (en) * | 2006-08-10 | 2010-08-10 | United Technologies Corporation | Ceramic shroud assembly |
US7665960B2 (en) | 2006-08-10 | 2010-02-23 | United Technologies Corporation | Turbine shroud thermal distortion control |
US7918642B2 (en) * | 2007-01-10 | 2011-04-05 | United Technologies Corporation | Instrument port seal for RF measurement |
CN103557079B (en) | 2008-10-08 | 2016-08-10 | 三菱重工业株式会社 | Gas turbine and method of operation thereof |
US8172521B2 (en) * | 2009-01-15 | 2012-05-08 | General Electric Company | Compressor clearance control system using turbine exhaust |
US8206085B2 (en) * | 2009-03-12 | 2012-06-26 | General Electric Company | Turbine engine shroud ring |
US8167546B2 (en) * | 2009-09-01 | 2012-05-01 | United Technologies Corporation | Ceramic turbine shroud support |
US8915701B2 (en) * | 2011-09-08 | 2014-12-23 | General Electric Company | Piping assembly and method for connecting inner and outer shell in turbine system |
CN102606312B (en) * | 2012-04-10 | 2014-07-09 | 北京航空航天大学 | Cooling method used for segmented geometric adjustment of guide vanes of gas turbine |
US9568009B2 (en) | 2013-03-11 | 2017-02-14 | Rolls-Royce Corporation | Gas turbine engine flow path geometry |
US9279339B2 (en) * | 2013-03-13 | 2016-03-08 | Siemens Aktiengesellschaft | Turbine engine temperature control system with heating element for a gas turbine engine |
WO2014143311A1 (en) * | 2013-03-14 | 2014-09-18 | Uskert Richard C | Turbine shrouds |
CN106460560B (en) * | 2014-06-12 | 2018-11-13 | 通用电气公司 | Shield hanging holder set |
CN106089324B (en) * | 2016-06-07 | 2018-05-01 | 中国南方航空工业(集团)有限公司 | stator casing sealing structure |
US10753232B2 (en) | 2017-06-16 | 2020-08-25 | General Electric Company | Assemblies and methods for cooling flowpath support structure and flowpath components |
US11111809B2 (en) * | 2018-05-14 | 2021-09-07 | Raytheon Technologies Corporation | Electric heating for turbomachinery clearance control |
US10760444B2 (en) | 2018-05-14 | 2020-09-01 | Raytheon Technologies Corporation | Electric heating for turbomachinery clearance control powered by hybrid energy storage system |
US10907501B2 (en) * | 2018-08-21 | 2021-02-02 | General Electric Company | Shroud hanger assembly cooling |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2047357A (en) * | 1979-04-27 | 1980-11-26 | Luk Lamellen & Kupplungsbau | Apparatus for selectively disconnecting and connecting a rotatable shaft |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH299035A (en) * | 1942-08-12 | 1954-05-31 | Vorkauf Heinrich | Cooled gas turbine rotor. |
US2402841A (en) * | 1944-06-26 | 1946-06-25 | Allis Chalmers Mfg Co | Elastic fluid turbine apparatus |
US2940660A (en) * | 1956-04-11 | 1960-06-14 | Alfred M Caddell | Compressor with air cooler between stages |
BE756582A (en) * | 1969-10-02 | 1971-03-01 | Gen Electric | CIRCULAR SCREEN AND SCREEN HOLDER WITH TEMPERATURE ADJUSTMENT FOR TURBOMACHINE |
US3807891A (en) * | 1972-09-15 | 1974-04-30 | United Aircraft Corp | Thermal response turbine shroud |
US4127357A (en) * | 1977-06-24 | 1978-11-28 | General Electric Company | Variable shroud for a turbomachine |
US4303371A (en) * | 1978-06-05 | 1981-12-01 | General Electric Company | Shroud support with impingement baffle |
GB2047354B (en) * | 1979-04-26 | 1983-03-30 | Rolls Royce | Gas turbine engines |
US4573865A (en) * | 1981-08-31 | 1986-03-04 | General Electric Company | Multiple-impingement cooled structure |
GB2117451B (en) * | 1982-03-05 | 1985-11-06 | Rolls Royce | Gas turbine shroud |
GB2125111B (en) * | 1982-03-23 | 1985-06-05 | Rolls Royce | Shroud assembly for a gas turbine engine |
US4573866A (en) * | 1983-05-02 | 1986-03-04 | United Technologies Corporation | Sealed shroud for rotating body |
US4553901A (en) * | 1983-12-21 | 1985-11-19 | United Technologies Corporation | Stator structure for a gas turbine engine |
FR2576637B1 (en) * | 1985-01-30 | 1988-11-18 | Snecma | GAS TURBINE RING. |
FR2597921A1 (en) * | 1986-04-24 | 1987-10-30 | Snecma | SECTORIZED TURBINE RING |
GB2206651B (en) * | 1987-07-01 | 1991-05-08 | Rolls Royce Plc | Turbine blade shroud structure |
-
1991
- 1991-03-11 US US07/666,959 patent/US5167487A/en not_active Expired - Lifetime
- 1991-12-26 IL IL100515A patent/IL100515A0/en unknown
-
1992
- 1992-01-08 DE DE69210077T patent/DE69210077T2/en not_active Expired - Fee Related
- 1992-01-08 EP EP92300154A patent/EP0503752B1/en not_active Expired - Lifetime
- 1992-01-09 JP JP4019345A patent/JPH0751888B2/en not_active Expired - Fee Related
- 1992-02-27 CA CA002061939A patent/CA2061939C/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2047357A (en) * | 1979-04-27 | 1980-11-26 | Luk Lamellen & Kupplungsbau | Apparatus for selectively disconnecting and connecting a rotatable shaft |
Also Published As
Publication number | Publication date |
---|---|
JPH04303104A (en) | 1992-10-27 |
DE69210077D1 (en) | 1996-05-30 |
EP0503752B1 (en) | 1996-04-24 |
CA2061939A1 (en) | 1992-09-12 |
DE69210077T2 (en) | 1996-12-19 |
US5167487A (en) | 1992-12-01 |
IL100515A0 (en) | 1992-09-06 |
EP0503752A1 (en) | 1992-09-16 |
CA2061939C (en) | 2002-05-28 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JPH0751888B2 (en) | Cooling shroud support | |
US5351478A (en) | Compressor casing assembly | |
US4379677A (en) | Device for adjusting the clearance between moving turbine blades and the turbine ring | |
JP5383973B2 (en) | System and method for exhausting used cooling air for gas turbine engine active clearance control | |
US4522557A (en) | Cooling device for movable turbine blade collars | |
JP4439053B2 (en) | Bay cooling turbine casing | |
JP2781413B2 (en) | Stator structure of gas turbine engine | |
US7527470B2 (en) | Stator turbine vane with improved cooling | |
US7823389B2 (en) | Compound clearance control engine | |
US4818178A (en) | Process for cooling the blades of thermal turbomachines | |
EP1213444B1 (en) | Shroud segment for a turbine | |
US7114914B2 (en) | Device for controlling clearance in a gas turbine | |
US5127795A (en) | Stator having selectively applied thermal conductivity coating | |
US4439982A (en) | Arrangement for maintaining clearances between a turbine rotor and casing | |
JP2007162698A5 (en) | ||
US20120006518A1 (en) | Mesh cooled conduit for conveying combustion gases | |
JPH0689653B2 (en) | Vane and packing clearance optimizer for gas turbine engine compressors | |
JP2004060656A (en) | Internal cooling of low pressure turbine case | |
EP1350018B1 (en) | Combustor turbine successive dual cooling | |
US6457316B1 (en) | Methods and apparatus for swirling fuel within fuel nozzles | |
US4439981A (en) | Arrangement for maintaining clearances between a turbine rotor and casing | |
GB1605255A (en) | Clearance control apparatus for bladed fluid flow machine | |
US20170030218A1 (en) | Turbine vane rear insert scheme | |
US3849022A (en) | Turbine blade coolant distributor | |
GB2244524A (en) | Clearance control in gas turbine engines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 19951212 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
LAPS | Cancellation because of no payment of annual fees |